Analysis of failed compressor blades from an aeroengine

The microfractographic features on the failed compressor rotor blades were largely obliterated due to post impact damages and the fire. The fracture pattern and the gross fractographic features indicate that the failures in the blades are secondary in nature and had occurred due to impact of the engine on to the ground. From the evidences, it appears most probable that the engine was on power at the time of impact